GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 670 AIRFOIL (goe670-il) Reynolds number: 100,000 Max Cl/Cd: 57.06 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe670-il-100000.txt Download as CSV file: xf-goe670-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 670 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4083 0.09528 0.09041 -0.0292 1.0000 0.1114
-7.750 -0.4366 0.09459 0.08987 -0.0276 1.0000 0.1123
-7.500 -0.4633 0.09336 0.08870 -0.0298 1.0000 0.1131
-7.250 -0.4764 0.08995 0.08531 -0.0308 1.0000 0.1140
-7.000 -0.4619 0.08578 0.08119 -0.0254 1.0000 0.1155
-6.750 -0.4573 0.08316 0.07860 -0.0223 1.0000 0.1177
-6.500 -0.4584 0.08069 0.07616 -0.0208 1.0000 0.1204
-6.250 -0.4617 0.07804 0.07351 -0.0209 1.0000 0.1239
-6.000 -0.4722 0.07475 0.06996 -0.0283 1.0000 0.1293
-5.750 -0.4655 0.07117 0.06653 -0.0241 1.0000 0.1310
-5.500 -0.4594 0.06889 0.06430 -0.0211 1.0000 0.1345
-5.250 -0.4534 0.06601 0.06103 -0.0267 1.0000 0.1448
-5.000 -0.4466 0.06250 0.05767 -0.0236 1.0000 0.1466
-4.750 -0.4382 0.06008 0.05528 -0.0216 1.0000 0.1499
-4.500 -0.4252 0.05719 0.05206 -0.0243 1.0000 0.1612
-4.250 -0.4160 0.05453 0.04950 -0.0222 1.0000 0.1641
-4.000 -0.4011 0.05232 0.04702 -0.0233 1.0000 0.1770
-3.750 -0.3908 0.05008 0.04490 -0.0212 1.0000 0.1818
-3.500 -0.3769 0.04803 0.04273 -0.0210 1.0000 0.1956
-3.250 -0.3533 0.04788 0.04218 -0.0227 0.9984 0.2224
-3.000 -0.3223 0.04445 0.03878 -0.0251 0.9927 0.2393
-2.750 -0.2576 0.03351 0.02551 -0.0308 0.9896 0.1134
-2.500 -0.2186 0.03147 0.02305 -0.0334 0.9838 0.1134
-2.250 -0.1842 0.02972 0.02092 -0.0349 0.9768 0.1135
-2.000 -0.1461 0.02790 0.01886 -0.0374 0.9714 0.1157
-1.750 -0.1136 0.02716 0.01809 -0.0388 0.9632 0.1221
-1.500 -0.0730 0.02653 0.01705 -0.0410 0.9573 0.1292
-1.250 -0.0429 0.02562 0.01617 -0.0419 0.9492 0.1360
-1.000 -0.0036 0.02506 0.01556 -0.0442 0.9432 0.1499
-0.750 0.0263 0.02456 0.01506 -0.0449 0.9347 0.1639
-0.500 0.0652 0.02416 0.01475 -0.0471 0.9285 0.1866
-0.250 0.0941 0.02382 0.01453 -0.0476 0.9193 0.2090
0.000 0.1352 0.02345 0.01438 -0.0501 0.9130 0.2415
0.250 0.1641 0.02315 0.01428 -0.0504 0.9033 0.2848
0.500 0.2565 0.02099 0.01402 -0.0628 0.9020 1.0000
0.750 0.2987 0.02099 0.01382 -0.0652 0.8917 1.0000
1.000 0.3564 0.02059 0.01327 -0.0700 0.8822 1.0000
1.250 0.3970 0.02023 0.01283 -0.0716 0.8691 1.0000
1.500 0.4361 0.01990 0.01244 -0.0730 0.8573 1.0000
1.750 0.4941 0.01928 0.01179 -0.0778 0.8521 1.0000
2.000 0.5218 0.01919 0.01168 -0.0774 0.8402 1.0000
2.250 0.5568 0.01890 0.01139 -0.0781 0.8303 1.0000
2.500 0.6022 0.01831 0.01083 -0.0804 0.8226 1.0000
2.750 0.6310 0.01806 0.01060 -0.0798 0.8099 1.0000
3.000 0.6632 0.01768 0.01024 -0.0797 0.7974 1.0000
3.250 0.6969 0.01723 0.00984 -0.0797 0.7844 1.0000
3.500 0.7290 0.01682 0.00947 -0.0795 0.7699 1.0000
3.750 0.7594 0.01642 0.00911 -0.0789 0.7527 1.0000
4.000 0.7915 0.01597 0.00869 -0.0785 0.7329 1.0000
4.250 0.8177 0.01571 0.00843 -0.0771 0.7076 1.0000
4.500 0.8461 0.01547 0.00815 -0.0761 0.6775 1.0000
4.750 0.8746 0.01542 0.00796 -0.0750 0.6402 1.0000
5.000 0.8947 0.01568 0.00804 -0.0727 0.5914 1.0000
5.250 0.9094 0.01607 0.00820 -0.0694 0.5333 1.0000
5.500 0.9239 0.01659 0.00841 -0.0664 0.4794 1.0000
5.750 0.9415 0.01731 0.00879 -0.0642 0.4419 1.0000
6.000 0.9613 0.01808 0.00934 -0.0627 0.4139 1.0000
6.250 0.9822 0.01884 0.00996 -0.0613 0.3915 1.0000
6.500 1.0039 0.01956 0.01061 -0.0602 0.3733 1.0000
6.750 1.0260 0.02028 0.01131 -0.0592 0.3573 1.0000
7.000 1.0471 0.02096 0.01197 -0.0580 0.3417 1.0000
7.250 1.0656 0.02157 0.01255 -0.0563 0.3243 1.0000
7.500 1.0829 0.02216 0.01309 -0.0545 0.3067 1.0000
7.750 1.1000 0.02275 0.01369 -0.0527 0.2902 1.0000
8.000 1.1143 0.02325 0.01427 -0.0504 0.2732 1.0000
8.250 1.1268 0.02372 0.01484 -0.0478 0.2554 1.0000
8.500 1.1375 0.02416 0.01538 -0.0449 0.2368 1.0000
8.750 1.1444 0.02461 0.01585 -0.0414 0.2157 1.0000
9.000 1.1451 0.02497 0.01636 -0.0369 0.1830 1.0000
9.250 1.1376 0.02620 0.01719 -0.0313 0.1165 1.0000
9.500 1.1340 0.02832 0.01891 -0.0270 0.0906 1.0000
9.750 1.1354 0.03019 0.02069 -0.0235 0.0797 1.0000
10.000 1.1428 0.03180 0.02239 -0.0207 0.0724 1.0000
10.250 1.1488 0.03375 0.02425 -0.0181 0.0675 1.0000
10.500 1.1626 0.03539 0.02604 -0.0162 0.0636 1.0000
10.750 1.1754 0.03700 0.02770 -0.0145 0.0596 1.0000
11.000 1.1969 0.03936 0.02993 -0.0140 0.0559 1.0000
11.250 1.2165 0.04138 0.03221 -0.0129 0.0541 1.0000
11.500 1.2370 0.04378 0.03485 -0.0121 0.0525 1.0000
11.750 1.2530 0.04631 0.03763 -0.0109 0.0512 1.0000
12.000 1.2630 0.04873 0.04025 -0.0092 0.0498 1.0000
12.250 1.2702 0.05127 0.04299 -0.0074 0.0487 1.0000
12.500 1.2810 0.05443 0.04625 -0.0065 0.0472 1.0000
12.750 1.2816 0.05806 0.05015 -0.0045 0.0468 1.0000
13.000 1.2743 0.06148 0.05386 -0.0021 0.0468 1.0000
13.250 1.2619 0.06478 0.05745 0.0004 0.0468 1.0000
13.500 1.2459 0.06828 0.06124 0.0025 0.0469 1.0000
13.750 1.2262 0.07187 0.06513 0.0040 0.0472 1.0000
14.000 1.2013 0.07633 0.06990 0.0046 0.0476 1.0000
14.250 1.1697 0.08193 0.07584 0.0037 0.0482 1.0000
14.500 1.1249 0.08991 0.08418 0.0001 0.0490 1.0000
14.750 1.0713 0.10131 0.09588 -0.0071 0.0504 1.0000
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Polar data table (+)
Polar graphs
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